MATEC Web of Conferences 115, 03001 (2017)
DOI: 10.1051/ matecconf/201711503001
STS-33
A mathematical model of metallized solid propellant combustion under the changing pressure Vasily Poryazov1,*, Aleksei Krainov1, and Dmitry Krainov2 1Tomsk
State University, Department of Physics and Engineering, 634050, Russia, Tomsk, 36 Lenin Ave. 2Tomsk Politechnical University, Institute of Power Engineering, Department of Theoretical and Industrial Heat Systems Engineering, 634050, Russia, Tomsk, 30 Lenin Ave.
Abstract. This paper presents the mathematical model describing a nonstationary combustion of metallized solid propellant. The model takes into account the heat transfer, the oxidizer decomposition and gasification of the solid propellant, two-phase, dual-velocity, two-temperature reactant flow over the propellant surface. The conditions on the surface perform the conservation of energy and mass fluxes. The model is based on the research works [1, 2]. Our research provides data of the non-stationary burning rate depending on the Al powder dispersion and the pressure drop value.
1 Mathematical model The mathematical formulation of the problem in the coordinate system associated with the propellant surface has the following form: The heat transfer and burn-out equations for condensed phase: E
1 T 2T T1 u 1 1 21 Q1k1 1 (1 )e RT1 , x x
t
1c1
(1)
E1
u k1 (1 )e RT1 . t x The system of equations for reactant flow over propellant surface:
T T2 v 2 x
t
2 c2
(2)
E
2 2T2 dp RT2
Q k Ye 4 r32 n(T3 T2 ) , 2 2 2 2 x 2 dt
(3)
E2
Y Y 2Y v D 2 k2Ye RT2 , t x x 2 2 v G , t x
(4) (5)
*
Corresponding author:
[email protected]
© The Authors, published by EDP Sciences. This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/).
MATEC Web of Conferences 115, 03001 (2017)
DOI: 10.1051/ matecconf/201711503001
STS-33
p
2 RT
,
(6)
T T 2 (7) c3 3 3 w 3 4 r32 n T3 T2 ) Al GQAl , 3O t x
3 ( 3 w) (8) G, t x w w (9) w fr , t x n (nw) (10) 0, t x The boundary conditions are: T x , t T x , t T1 , t T2 , t 0,
1 1 s 2 2 s , T1 xs , t T2 xs , t , 0, x x x x Y , t 0 , Al 1u 3 w( xs , t ) , 2 ( xs , t ) P RT2 ( xs , t ) x (11) n( xs , t ) 3 ( xs , t ) 4 rAl3 ,0 k , 3 Y xs , t (1 Al ) 1u ( 2 vY ) x ,t D 2 xs , t , (1 Al ) 1u 2 xs , t v xs , t . s x The initial conditions are: (12) x xs : T1 x, 0 T0 , x, 0 0 ,
xs x : T x, 0 Tig , Y x, 0 0 , v x,0 0 , p 0 p0
(13)
2 x, 0 p0 RTig , 3 x, 0 0 , w x, 0 0 , n x, 0 0 . The particle interaction force with the gas is defined by the formula: tr Ftr ( 4 3 r33 k ) , Ftr CR Sm 2 w u u w / 2 . The drag coefficient is defined by the empirical formula [3]: CR 24 1 0,15 Re 0,682 , Re 2rk 2 u w . Re The heat transfer coefficient is determined as: Nu 2 2r , Nu 2 Nul 2 Nut 2 , k where Nul 0, 664 Re
0,5
, Nut 0, 037 Re
0,8
(14) (15)
(16)
.
The mass-change rate of particles during combustion: 3O G n k 4 k Al a 0.9 rAl1.5 , k Al 2.22 105 m1.5 s . 2 Al
(17)
The radius of unburnt aluminum particle rAl and the radius of a whole particle: 1
2 3 3 Al 3 2 O 3 3 3 rAl Al (1 O )rAl3 ,0 rAl ,0 rAl3 (18) , r3 rAl n 3 2 4 3 k O
Al Al The pressure drop value ranges from p0 (at t p , n - start drop time) to pk at the end of the 13
drop ( t p , k ). The linear combustion rate u is the rate of conversion level 0.99 motion.
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MATEC Web of Conferences 115, 03001 (2017)
DOI: 10.1051/ matecconf/201711503001
STS-33
Fig. 2. Burning rate of N powder with micron sized aluminum particles in time. Pressure drop ranges from 100 atm to: 1 80, 2 - 70, 3 – 60, 4 – 50, 5 – 40, 6 – 30, 7 – 20 atm. Pressure drop rate 1010 Pa / s ,
Fig. 1. Burning rate of N powder with micron sized aluminum particles in time. Pressure drop ranges from 100 atm to: 1 - 80, 2 - 60, 3 – 50, 4 – 40, 5 – 30, 6 – 20 atm. Pressure drop rate 1010 Pa / s , rAl 5 mkm
rAl 15 mkm
Fig. 3. Burning rate of N powder with micron sized aluminum particles in time. From 100 atm to: 1 - 80, 2 - 70, 3 – 60, 4 – 50, 5 – 40, 6 – 30, 7 – 20 atm. Pressure drop rate r 30 mkm 1010 Pa / s , Al
Fig. 4. Burning rate of N powder in time. Pressure drop ranges from 100 to: 1 - 80, 2 - 40, 3 – 20 atm. Pressure drop rate 1010 Pa / s
Here: t is the time, x is the coordinate, xs is the coordinate of combustion surface, 1 , , 2 3 , Al , k is the density of solid propellant, gas, reduced density of particles, aluminum, particle in the flow of combustion product, T1 , T2 , T3 is the temperature of solid propellant, gas phase, aluminum particles in gas phase, T0 , Tig is the initial temperature of solid and gas phases, is the conversion degree of the condensed-phase material, u is the linear combustion rate, v , w is the gas velocity and particle velocity, n is the number of particles in a unit volume, rAl , r3 is the radius of unburnt particle of aluminum and the whole radius of a particle, c1 , c2 , c3 is the specific heat of solid propellant, gas and
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MATEC Web of Conferences 115, 03001 (2017)
DOI: 10.1051/ matecconf/201711503001
STS-33
particles at a constant pressure, is the thermal conductivity, Q1 is the thermal effect of reaction in the solid phase, Q2 — thermal effect of reaction in the gas phase, QAl — heat of aluminum combustion, k is the pre-exponential factor in the Arrhenius law, E is the energy of activation, R is the universal gas constant, Al is the is the aluminum mass fraction in solid propellant, p is the gas phase pressure, p0 , pk is the initial and final pressure in gas phase , t p , n , t p , k is the start and end time of pressure drop, Y is the oxidant concentration in the gas phase, D is the diffusion coefficient, , Al , O is the molar masses of gas phase, aluminum particles and oxygen, G is the massis thechange rate of particles during combustion, fr is the particle interaction force with the gas, is the heat transfer coefficient. The quantities related to the condensed phase are denoted by index 1, to the gas is the 2, to particles is the 3, to the initial conditions is the 0. We have solved the system of equation numerically using the methods described in the papers [1,2]. The calculations of N powder combustion of with micron sized aluminum particles were carried out at the following values of the thermophysical and kinetic quantities from [1,2] We have conducted the calculation of the non-stationary burning rate during the pressure drop over the propellant surface. The composition combusts stationary under the pressure of 100 atm, at the time of 40 ms the pressure over the surface begins to drop in linear fashion at the rate of 1010 Pa / s . The values of the final pressure are 80, 70, 60, 50, 40, 30 and 20 atm. The size of Al particles varies from 5 to 30 mkm (Pic.1, Pic.2, Pic. 3). The combustion rate during the pressure drop is less than under the final pressure. Pic. 4 shows the combustion rate of non-metallized N powder. One can see in the picture that the combustion attenuates, when the pressure drops to 20 atm. In comparison to the pattern for metallized N powder, the addition of Al particles increases the combustion stability and the particle size growth reduces the time of transient interval.
Conclusion We developed the mathematical model of metallized solid propellant non-stationary combustion. The statement of the problem includes the heat transfer, the oxidizer decomposition and gasification of the solid propellant, two-phase, dual-velocity, twotemperature reactant flow over the propellant surface. The model takes into account the diffusion and the exothermal reaction in gas phase, heating and combustion of Al particles in the flow, the particle velocity lag relative to the gas. The conditions on the surface perform the conservation of energy and mass fluxes. The paper provides data of nonstationary combustion under decreasing pressure. The work investigates transient-state conditions depending on the pressure change and the size of Al particles in solid propellant. This work was carried out with financial support from President of Russian Federation grant МК1763.2017.8..
References 1. A.Y. Krainov, D.A. Krainov, V.A. Poryazov, J. Eng. Phys. Thermophys. 89, 458 (2016) 2. A.Y. Krainov, V.A. Poryazov, Combust., Explosion and Shock Waves 51, 664 (2015)
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MATEC Web of Conferences 115, 03001 (2017)
DOI: 10.1051/ matecconf/201711503001
STS-33
3. Spravochnik po teploobmennikam. V dvukh tomakh. 1. M .: Energoatomizdat, 1987. [in Russian]
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